发动机加力燃烧室湍流流场数值计算

NUMERICAL COMPUTATION ON TURBULENT REACTING FLOW IN AEROENGINE AFTERBURNER

采用非正交曲线坐标系下非交错网格的ＳＩＭＰＬＥ方法，对航空发动机加力燃烧室气相燃烧的湍流流场进行了数值计算，湍流模型采用ｋ－ε双方程模型，平均化学反应速率采用涡旋破碎模型（ＥＢＵ）计算，对ＥＢＵ模型的缺陷作了讨论。差分网格采用分区方法生成，计算时对整个流场进行分区迭代直至得到收敛结果，数值计算结果合理。

The turbulent reacting flow in an afterburner with stabilizers was calculated using the SIMPLE method under curvilinear coordinate with zonal grid.The turbulence model was k ε model and the average chemical reacting rate was calculnated using the EBU model.Computation was conducted on all zones until the iteration was arrived.The turbulent reacting flow in an aircraft afterburner with three V stabilizers was computed and the results were reasonable